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liquid propellant rocket propulsion systems
相关语句
  液体火箭推进系统
     Modeling and simulations of the failure process for liquid propellant rocket propulsion systems
     液体火箭推进系统故障过程建模与仿真研究
短句来源
     To overcome the difficulties on acquiring enough fault modes from ground and flight test data, the failure process for liquid propellant rocket propulsion systems was modeled.
     为克服由于试验或飞行数据不足而无法获取系统足够故障模式的问题 ,开展了液体火箭推进系统故障过程建模与计算机仿真研究工作。
短句来源
  相似匹配句对
     Evolution of Quality Analysis for Liquid Propellant
     液体推进剂质量分析发展综述
短句来源
     DROPLET DISPERSION IN LIQUID PROPELLANT GUNS
     液体发射药火炮中液滴散布的理论研究
短句来源
     REVIEW OF LIQUID PROPELLANT ROCKET ENGINE
     液体火箭发动机技术的回顾与展望
短句来源
     Research on Dynamics of Large Liquid Propellant Rocket
     大型液体火箭动力学课题研究
短句来源
     Data Analysis and Processing on Liquid Propellant of Rocket
     火箭液体推进剂数据分析与处理
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To overcome the difficulties on acquiring enough fault modes from ground and flight test data, the failure process for liquid propellant rocket propulsion systems was modeled. For a specific model system, a uniform description method of system failures was used to develop the equations for describing failures of the model system. Since the equations are very stiff and nonlinear, the Runge Kutta method with a variable step and the Treanor method was used respectively to solve the equations....

To overcome the difficulties on acquiring enough fault modes from ground and flight test data, the failure process for liquid propellant rocket propulsion systems was modeled. For a specific model system, a uniform description method of system failures was used to develop the equations for describing failures of the model system. Since the equations are very stiff and nonlinear, the Runge Kutta method with a variable step and the Treanor method was used respectively to solve the equations. The large number of examples from the computer simulations of the system failures were compared with the results of fire tests, and results demonstrate that the model and methods developed in this research are sound and valid.

为克服由于试验或飞行数据不足而无法获取系统足够故障模式的问题 ,开展了液体火箭推进系统故障过程建模与计算机仿真研究工作。结合具体的模型系统 ,研究了各组件统一的故障描述方法 ,形成了表征系统故障过程的方程组。针对故障方程组的超强刚性和非线性特性问题 ,研究了解决该问题的数学方法。给出了系统故障过程的具体仿真实例以及与实际试车结果的对比分析 ,结果表明所建模型和数值求解方法对于研究液体火箭推进系统的故障过程是合理和有效的

 
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